One of the major challenges of Mini-Unmanned Aerial Vehicle flight is the unsteady interaction with turbulent environment while flying in lower levels of atmospheric boundary layer. Following inspiration from nature we expose a new system for angle of attack estimation based on pressure measurements on the wing. Such an equipment can be used for real-time estimation of the angle of attack during flight or even further building of wind velocity vector with additional equipment. Those information can find purpose in control and stabilization of the aircraft due to inequalities seen by the wing or even for various soaring strategies that rely on active control for energy extraction. In that purpose, flying wing aircraft has been used with totally four span-wise locations for local angle of attack estimation. In-flight angle of attack estimation from differential pressure measurements on the wing has been compared with magnetic sensor with wind vane. The results have shown that pressure ports give more reliable estimation of angle of attack when compared to values given by wind vane attached to a specially designed air-boom. Difference in local angle of attack at four span-wise locations has confirmed spatial variation of turbulence in low altitude flight. Moreover, theoretical law of energy dissipation for wind components described by Kaimal spectrum has shown acceptable match with estimated ones.

中文翻译：

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仿生风场估计——第 1 部分：通过表面压力分布测量攻角

微型无人机飞行的主要挑战之一是在大气边界层的较低水平飞行时与湍流环境的不稳定相互作用。遵循自然的灵感，我们展示了一种基于机翼压力测量的攻角估计新系统。这种设备可用于在飞行过程中实时估计迎角，甚至可以通过附加设备进一步构建风速矢量。由于机翼所见的不平等，这些信息可以用于控制和稳定飞机，甚至可以用于依赖主动控制来提取能量的各种飙升策略。为此，飞翼飞机已经使用了总共​​四个展向位置来估计局部迎角。从机翼上的压差测量估计的飞行迎角已与带风向标的磁传感器进行了比较。结果表明，与连接到专门设计的空气臂的风向标给出的值相比，压力端口可以更可靠地估计迎角。四个展向位置的局部迎角差异证实了低空飞行中湍流的空间变化。此外，Kaimal 谱描述的风分量能量耗散的理论规律与估计值一致。结果表明，与连接到专门设计的空气臂的风向标给出的值相比，压力端口可以更可靠地估计迎角。四个展向位置的局部迎角差异证实了低空飞行中湍流的空间变化。此外，Kaimal 谱描述的风分量能量耗散的理论规律与估计值的匹配是可以接受的。结果表明，与连接到专门设计的空气臂的风向标给出的值相比，压力端口可以更可靠地估计迎角。四个展向位置的局部迎角差异证实了低空飞行中湍流的空间变化。此外，Kaimal 谱描述的风分量能量耗散的理论规律与估计值的匹配是可以接受的。